![supercritical airfoil supercritical airfoil](https://www.nasa.gov/centers/dryden/images/content/110331main_supercritical1_330.jpg)
The overall low speed performance of supercritical CFJ airfoils is significantly superior to conventional super-critical airfoils. Whereas the CFJ-RAE-2822 and CFJ-NASA SC(2)-1010 airfoils achieve lower maximum lift coefficient of 5.4 and 5.9 respectively. This study indicates that the CFJ-NASA-SC(2)-0714 supercritical airfoil is able to achieve super-lift coefficient of 9.1 at Mach 0.1, attributed to its large leading edge radius and airfoil thickness. It is found that for the CFJ supercritical airfoils, very high maximum lift coefficient is obtained while improving the aerodynamic efficiency at cruise at low angle of attack(AoA). Numerical studies are carried out to investigate the effects of slots location and size, airfoil thickness, and jet intensity on the low speed performance of the airfoil. The simulations employ the intensely validated in-house CFD solver, FASIP, using Reynolds Averaged Navier-Stokes(RANS) equations with one-equation Spalart- Allmaras turbulence model. The results are very encouraging to achieve high lift coefficient for takeoff/landing without using the conventional flap systems.Ībstract = "This paper studies the low-speed performance of coflow jet (CFJ) supercritical airfoils based on three baseline supercritical airfoil of NASA SC(2)-1010, RAE-2822, and NASA SC(2)-0714. 7 refs., 12 figs.This paper studies the low-speed performance of coflow jet (CFJ) supercritical airfoils based on three baseline supercritical airfoil of NASA SC(2)-1010, RAE-2822, and NASA SC(2)-0714. In contrast, the thin airfoil family was designed to reduce peak power at optimum blade pitch to minimize blade loads and maximize annual energy output. By operating the wind turbine at a less desirable blade pitch angle, peak power can be reduced at the expense of higher mean blade loads and lower annual energy output. The results of the study show that fixed-wing airfoils generally result in excessive peak power for stall regulated, rigid rotors.
#SUPERCRITICAL AIRFOIL CODE#
Resulting annual energy output, which is dependent on the wind-speed distribution, was calculated using SERI's Systems Engineering and Analysis Computer Code (SEACC). After generating the performance characteristics for each airfoil series, the subsequent rotor performance and blade loads were calculated using SERI's PROPSH computer code. On a relative basis, this approach to comparing airfoils was considered more accurate than using airfoil performance characteristics based on wind-tunnel test data.
#SUPERCRITICAL AIRFOIL SERIES#
The performance characteristics of the different airfoil series more » were derived analytically using the Eppler airfoil design code in the analysis mode. The Micon 110 wind turbine was chosen because it is a typical three-bladed, stall-regulated rigid rotor system. The traditional airfoil series chosen for comparison with SERI's new thin airfoil family were the NACA 23XXX, NACA 44XX, and NASA LS(1).
![supercritical airfoil supercritical airfoil](https://ars.els-cdn.com/content/image/1-s2.0-S1000936120300881-gr8.jpg)
The objective of this study was to compare the performance characteristics of one of these airfoil families to other commonly used airfoil series for a typical three-bladed, stall-regulated HAWT. At the Solar Energy Research Institute (SERI), new airfoils have been developed to help improve the performance and economics of horizontal-axis wind turbines (HAWTS).